Multi-orientation, advanced vertical agility, variable-environment vehicle

ABSTRACT

A vertical takeoff and landing craft that utilizes lifting, propulsion and maneuvering (LPM) assemblies comprising a series of blade foils arranged along track elongated loop paths disposed at the sides of a fuselage. These LPM assemblies are provided with control mechanisms enabling lift, attitude changes, altitude changes and directional flight propulsion and control including those needed for hovering as well as vertical takeoff and landing. The LPM assemblies are configured to drive large volumes of air in a manner and scale favorably similar to conventional rotorcraft while in contrast, providing capability for faster flights by eliminating or minimizing speed limiting factors commonly associated with rotorcraft.

CROSS-REFERENCE TO RELATED APPLICATIONS

This application is a continuation of application Ser. No. 13/914,120filed Jun. 10, 2013, which application is hereby incorporated herein byreference in its entirety and from which application priority is herebyclaimed under 35 U.S.C. §120.

BACKGROUND

Embodiments are in the field of air, sea and land vehicles. Moreparticularly, embodiments are in the field of vertical take-off andlanding vehicles. More particularly still, embodiments are directedtowards vehicles combining the mass flow generating capabilities ofrotorcraft for hover and low speed load carrying capabilities with thespeed, range and altitude capabilities of high speed fixed wing craft.

SUMMARY

One embodiment comprises a craft comprising a fuselage flanked bylifting, propulsion and maneuvering units (LPM assemblies). Componentsof each of the LPM assemblies may comprise a plurality of individualdiscrete wing blades or airfoils (hereafter, “blade foil” or “bladefoils”) arranged about an elongated loop path set on edge. According toone embodiment, such blade foils cycle around the elongated loop path ina longitudinal and vertical plane, to produce desired forces forlifting, propulsion and maneuvering. A control assembly enables bladefoils to attain high-flow angles of attack such that all needed lift,maneuverability, attitude changes, stability, altitude changes andpropulsion may be provided solely by the blade foils. According to oneembodiment, the control assembly enables the blade foils to achievefunctional high-flow angles of attack at all or substantially all pointsalong the elongated loop path and to maintain desirable blade foilangles with respect to relative flow, including the extreme ends of theelongated loop paths. In such an embodiment, while moving the bladefoils from back to front on the top portion of the elongated loop pathand following around to the bottom portion of the elongated loop path,then from front to back, pitch angles and chord lengths may be selectedtop relative to bottom to achieve lift, forward flight and aft flight aswell as directional changes, across a range speeds and strengths. In oneembodiment, the lower surfaces of the blade foils are maintained as thelower surfaces continuously and throughout the entire cycle aroundelongated loop path. Likewise, the top surfaces of the blade foils aremaintained as the top surfaces (meaning the top surfaces face upwards)throughout their entire path around the elongated loop path. In thismanner, all needed forces may be solely and completely provided simplyby controlling power to the blade foils and the pitch angles of anindividual blade foil or collective thereof blade foils as they aremoved around the elongated loop path.

According to one embodiment, if the pitch angles of the blade foils onthe top portion of the elongated loop path are controlled to assume ashallow pitch angle, and the pitch angles of the blade foils travelingalong the bottom path of the elongated loop path are moved to a morecoarse or steep pitch angle, (meaning closer to a perpendicular anglerelative to their direction of travel, front to back), then the craftwould move forward, assuming the LPM assemblies on each side of thecraft were cycling around their elongated loop paths at the same speedswith the same pitch combinations. Any variation, side to side, and/ortop to bottom of each LPM assembly, effectively changes attitude,horizontal and vertical maneuvers and/or speed in all directions andcombinations about the three x, y and z axes. According to oneembodiment, assuming that the cycling speeds around the elongated looppaths are sufficient to generate more lift than the weight of the craft,which may according to embodiments include lighter than air componentsto provide a degree of lifting force, and assuming that the angles ofpitch and combined surface areas of the blade foils are likewisesufficient to produce that lift, then such a craft would rise inaltitude. If the elongated loop path on the starboard side of such acraft were given more power and a higher speed of revolution relative tothe elongated loop path on the port side of the craft, or more pitch,aggregate blade foil surface area or some combination thereof, then thecraft would tend to bank to port and also turn to port (rotate in thevertical plane to port). According to one embodiment, if a certainsection including a plurality of blade foils were given a coarser orsteeper pitch relative to another or other section(s) along an LPMassembly, then that section of the LPM assembly and the portion of thefuselage nearest that section would both be lifted upwards and propelledin a direction opposite the direction of travel of the blade foils whosepitch has been steepened. In this manner, multiple attitudes and acontinuum of combinations of lift, direction of travel and attitude maybe controlled using simple pitch changes in a sub-region (a regionsmaller than an entire top or bottom of a elongated loop path) combinedwith changes in the speed and/or power applied to the LPM assemblies.LPM assemblies and their constituent blade foils may be arranged inconfigurations and locations to enable the placement of other structuresand controls to influence in-flows and out-flows of the LPM assembliesand their constituent blade foils and to permit movement of LPMassemblies as a whole, independently from and relative to a fuselage andan LPM assembly on the opposite side of the fuselage.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is an overhead perspective view of a craft comprising a fuselagein the center, flanked on either side with two LPM assemblies, eachcomprising a plurality of individual blade foils, arranged inlongitudinal file about two, bilaterally symmetrical, horizontallylaid-out elongated loop paths, according to one embodiment.

FIG. 2 is a side view of the craft of FIG. 1, showing details of anelongated loop path on the port side of the craft, and further showingmultiple blade foils, arranged around a track as well as a control unit,according to one embodiment.

FIG. 3 is a perspective view of a craft of FIG. 1, showing upper leadingedge slats, upper trailing edge flaps, lower blade foil leading edgeslats, lower trailing, edge flaps, along with an elongated cone-shapedcontrol track and driving track, according to one embodiment.

FIG. 4 comprises a series of perspective views of individual upper trackblade foils with leading edges indicated for clarity and showing controltrack assembly including wedge slide control blocks as well asconnecting rod followers. Also shown are control arms, belt track andblade foil pivot axle, according to one embodiment.

FIG. 5 comprises a series of perspective and cross-section views ofindividual lower track blade foils connecting rods, control arms, bladefoil pivot axles and wedge slide control blocks with the leading edgesof the blade foils indicated for clarity, according to one embodiment.

FIG. 6 is a port side view of the craft of FIG. 1 showing an elongatedcone-shaped control track in low pitch position, closer lateral to afuselage, as well as blade foils and driving track, according to oneembodiment.

FIG. 7 is a side view of the craft of FIG. 1 with the elongatedcone-shaped control track removed for clarity, showing blade foils inangles resulting from low pitch position of control loop unit as shownin FIG. 6, according to one embodiment.

FIG. 8 is a head-on view of the craft of FIG. 1, showing blade foils incross-section and control arms in angles resulting from low pitchposition of control loop (not shown here for clarity) as shown in FIG.6, as well as the fuselage, according to one embodiment.

FIG. 9 is a side view of the craft of FIG. 1, showing an elongatedcone-shaped control track in a high pitch position, laterally fartherfrom a fuselage, as well as blade foils and driving track, according toone embodiment.

FIG. 10 is a side view of the craft of FIG. 1, with the elongatedcone-shaped control track removed for clarity, showing blade foils inangles resulting from high pitch position of control loop unit as shownin FIG. 9, according to one embodiment.

FIG. 11 is a head-on view of the craft of FIG. 1, showing blade foils incross-section and control arms in angles resulting from high pitchposition of control loop (not shown here for clarity) as shown in FIG.9, as well as fuselage according to one embodiment.

FIG. 12 is a side view of the craft of FIG. 1, showing the elongatedcone-shaped control track in a raised position relative to drivingtrack, resulting in higher pitch angles of blade foils along the lowertrack portion of an LPM assembly, and flatter (lower) pitch angles ofthose blade foils along the upper track portion of the LPM assembly,according to one embodiment.

FIG. 13 is a side view of the craft of FIG. 1 with the elongatedcone-shaped control track removed for clarity, showing blade foils indifferential pitch angles for an upper blade foil group relative to alower blade foil group, resulting from a raised position of theelongated cone-shaped control track as shown in FIG. 12 according to oneembodiment.

FIG. 14 is a head-on view of the craft of FIG. 1 showing blade foils incross-section and elevated angles of control arms resulting from highposition of the elongated cone-shaped control track (not shown here forclarity) relative to driving track as shown in FIG. 12, as well asfuselage according to one embodiment.

FIG. 15 is a side view of the craft of FIG 1 showing the elongatedcone-shaped control track in a lowered position relative to drivingtrack resulting in lower pitch angles of blade foils along the lowertrack portion of LPM assembly, and higher pitch angles of those bladefoils along the upper track portion of the LPM assembly, according toone embodiment.

FIG. 16 is a side view of the craft of FIG. 1 with the elongatedcone-shaped control track removed for clarity, showing blade foils indifferential pitch angles for an upper blade foil group relative to alower blade foil group, resulting from lowered position of the elongatedcone-shaped control track as shown in FIG. 15, according to oneembodiment.

FIG. 17 is a head-on view of the craft of FIG. 1 showing blade foils incross-section and elevated angles of control arms resulting from lowposition of the elongated cone-shaped control track (not shown here forclarity) relative to driving track as shown in FIG. 15, as well asfuselage, according to one embodiment.

FIG. 18 is a side view of the craft of FIG. 1 showing the elongatedcone-shaped control track in an angled position longitudinally relativeto driving track such that the elongated cone-shaped control track isshown lowered towards the front of the craft of FIG. 1, and in a neutralposition vertically, aft resulting in higher pitch angles of blade foilsalong the forward upper track portion of the LPM assembly, and neutralpitch angles of those blade foils along the rest of the track portionsof the LPM assembly, according to one embodiment.

FIG. 19 is a side view of the craft of FIG. 1 with the elongatedcone-shaped control track removed for clarity, showing blade foils indifferential pitch angles for an upper forward blade foil group relativeto the rest of the blade foil groups all along the other track portionsof an LPM unit, resulting from a rotated position of the control loopunit as shown in FIG. 18 according to one embodiment.

FIG. 20 is a top down view of an LPM assembly showing short span, sweptleading edge blade foils in a non-extended span configuration, accordingto one embodiment.

FIG. 21 is a top down view of an LPM assembly showing extended span(“telescoped” outboard) blade foils configuration, according to oneembodiment.

FIG. 22 is a side view of the craft of the present embodiments showingstator vanes over, between forward of, aft of and under blade foils,according to one embodiment.

FIG. 23 is a perspective overhead view of the craft of FIG. 1illustrating stator vanes, according to one embodiment.

FIG. 24 is a perspective underside view of the craft of FIG. 1,illustrating stator vanes, according to one embodiment.

FIG. 25 is an underside perspective view of an alternate configurationof an LPM assembly showing drive track, blade foils with leading edgesand control tines, according to one embodiment.

FIG. 26 is an underside perspective view of an alternate configurationof an LPM assembly showing drive track, blade foils with leading edges,and control tines, according to one embodiment. Also shown are partialupper and lower sections of control track, according to one embodiment.

FIG. 27 is a side view line drawing of an alternate configuration of theLPM assembly of FIG. 25, showing forward fairing and aft fairing,according to one embodiment.

FIG. 28 is a side perspective view of a craft according to oneembodiment showing drive wheels, fan driving wheels, idler wheelsdriving track, elongated cone-shaped control track and stator vanes,according to one embodiment.

FIG. 29 is a front perspective of the craft of FIG. 1 showing fuselageand splayed out LPM assemblies, fan drive wheels, blade foils, statorvanes, drive wheels, idler wheels and elongated cone-shaped controltracks, according to one embodiment.

FIG. 30 is an overhead view of the craft of FIG. 1, showing fuselage,multiple protective stator vanes, upper track blade foils with leadingedge slats, elongated cone-shaped control track, and control arms,according to one embodiment.

FIG. 31 are overhead views of the craft of the current embodimentsshowing deployment of movable wings in various positions as well as LPMassemblies in various positions, according to one embodiment.

FIG. 32 is an overhead, viewing forward to aft perspective view of thecraft of FIG. 1, showing movable wings, LPM assemblies with blade foils,stator vanes, drive tracks, fan drive wheels and wine flaperons,according to one embodiment.

FIG. 33 is an overhead, viewing aft to forward perspective view of thecraft of FIG. 1, showing movable wings, LPM assemblies with fan drivewheels and wing flaperons, according to one embodiment.

FIG. 34 is an underside perspective view of the craft of FIG. 1, showingwing extension track, movable wines, flaperons and fan drive wheels,according to one embodiment.

FIG. 35 is a front view of the craft of FIG. 1 showing fuselage, drivewheels, protective stator vanes, control arms, elongated cone-shapedcontrol track, blade foils and drive tracks of bilateral LPM assembliescanted outboard at the bottom, according to one embodiment.

FIG. 36 is a side view of the craft of FIG. 1 with a physical controlelement not shown for clarity, showing a driving track, blade foils withthickened chords along bottom sections of an LPM assembly and bladefoils with normal chords along top sections of art LPM assembly,according to one embodiment.

FIG. 37 is a closer-up view of a section of the craft of FIG. 1 with acontrol element removed for clarity, showing a drive track, blade foilswith normal chord along top sections of an LPM assembly and blade foilswith thickened chord along bottom sections of an LPU, according to oneembodiment. Also shown is an enlarged view with control element removedfor clarity, of a partial section of drive track, an idler wheel,control arm, blade foil with thickened chord, deployed leading edgeslat, deployed trailing edge flap and camber cam, according to oneembodiment.

DETAILED DESCRIPTION

The most efficient mechanism for lifting heavy loads, other thanlighter-than-air craft such as lifting balloons, and various forms ofrigid structure lighter-than-air craft, is to move large volumes of airrelatively slowly, as opposed to moving small volumes of air atrelatively high speeds. The present embodiments, although relativelycompact in size, comprise functional and controllable systems thatselectively move large volumes of air at low and/or high speeds. Thepresent embodiments are configured to move large volumes of relativelycool, ambient air or other media at relatively low speeds for relativelyefficient, heavy lifting capabilities, as compared to turbofans, turboprops and other vertical lift systems. In fact, the present embodimentsoffer speed and efficiency performance capabilities currently onlyassociated with high speed fixed wing craft by enabling the operator tocycle between choosing to move large volumes of air in oneconfiguration, then seamlessly transitioning to other configurations tomove smaller volumes of air at higher velocities and back again in acontinuum of available configurations.

Turning now to the figures, FIG. 1 shows a craft 100 comprising afuselage 10 flanked by lifting, propulsion and maneuvering (LPM)assemblies 11 arranged with one LPM assembly 11 on each side extendingfor example approximately the length of the fuselage 10, according toone embodiment. Each of these LPM assemblies 11 comprise a plurality ofindividual, discrete wings, blades or foils (hereafter, collectively,“blade foils”) 12, arranged about a (e.g., a generally ovaloid orelliptical shape that may comprise flat segments) elongated loop path 13to produce the desired forces for lifting, propulsion and maneuveringthe craft. The elongated loop path 13, according to one embodiment, maybe configured to have a greater dimension along a longitudinal axis ofan elongated fuselage than perpendicular thereto. Stated differently,when the craft is flying parallel to level ground, the dimension of theelongated loop path perpendicular to the force of gravity may be greaterthan the dimension of the elongated loop path that is parallel to theforce of gravity. It is to be noted that the fuselage 10 in the figuresis a generic fuselage that may be adapted according to the desiredfunctionality and mission to which the craft 100 is destined. As such,the depicted simplified shape and appearance of the fuselage 10functions merely as a placeholder which, it is to be expected, will varyaccording to the nature and purpose of the craft 100. According to oneembodiment, such a craft may accommodate a human pilot, be controlledautonomously or semi-autonomously by software or be controlled by aremote human pilot. Accordingly, it is to be understood that embodimentscover both piloted and drone aircraft or other media vehicle and/or anycombination thereof.

By moving the blade foils 12 from back to front on a first portion(e.g., the top portion) of an elongated loop path 13, as shown in FIG.2, and following around to a second portion (e.g., the bottom portion)of the elongated loop path 13, then from front to back, pitch angles maybe selected at the top of the elongated loop path 13 relative to thebottom of the elongated loop path 13 to thereby achieve lift, forwardflight and aft flight at any combination of attitude, altitude andspeed, depending on available power. If, for example, the pitch anglesof the blade foils 12 on the top of elongated loop path 13 were to becontrolled to be shallow, and those along the bottom path of elongatedloop path were to be controlled to be steeper (i.e., oriented at arelatively greater pitch angle), or more perpendicular to theirdirection of travel (front to back), then the craft would move forwardassuming the blade foils of the LPM assemblies 11, on each side of thecraft, were moving around their respective elongated loop paths 13 atsubstantially the same speeds with substantially the same pitch andpower. Assuming the speeds of revolution along elongated loop paths 13were sufficient to generate more lift than the weight of the craft 100and the pitch angles were likewise sufficient to produce that lift, thenthe craft 100 of FIG. 1 would also rise in altitude. If, on the otherhand, the LPM assembly 11 on the elongated loop path 13 on the starboardside of the craft 100 were given more power and thus driven at a higherspeed of revolution relative to the LPM assembly 11 on the elongatedloop path 13 on the port side of the craft 100, or more pitch, or both,then the craft 100 may tend to bank to port and also turn to port(rotate in the vertical plane to port). Advantageously, embodimentsexhibit less, if any, adverse yaw as compared with conventional fixed orrotary winged crafts, since increasing power and speed of rotationand/or greater pitch may pull the affected side around, and may also maytend to bank the craft in the same direction, such as may occur in atwin engine fixed wing craft assuming the pilot or flight computerincreased thrust in the engine on the same side as the aileron islowered for a coordinated, banking turn. Embodiments shown in FIG. 1 etseq. may be configured to enable automatic, coordinated, safe turns ineither direction at virtually any speed simply by increasing power tothe flanking LPM assembly 11 that is opposite to the desired turn andbank. The same applies, according to one embodiment, to differentialpitch changes, for one flanking LPM assembly 11 relative to itscounterpart LPM assembly 11 on the opposite side of the fuselage.

According to embodiments, structures that favorably affect handling,stability and enable simpler control units construction compared withrotorcraft particularly, are those related to optimal direction ofgyroscopic forces as created by movements of LPM assemblies 11configured according to their placements along fuselage 10. Indeed, byaltering the pitch angles of blade foils 12 at various points along theelongated loop paths 13, with or without changing the orientationsand/or positions of the LPM assemblies 11 with respect to a fuselage 10,nearly any and all flight attitudes and holding attitudes in hover are,according to one embodiment, attainable. These combinations anddifferential effects enable for example, nose up, nose down or levelattitudes in hover and for trimming purposes in directional flight,which may be used to gain variations in visibility both in flight and inhover and for balancing load positions aboard or in sling loads amongfunctionalities. Assuming that the pitch to the forward half of thebottom pathway blade foils 12 is increased while keeping all other bladefoils 12 in their then current pitches and orientations, the craft 100would be placed in a climbing, nose high attitude. If the pitch anglesof the blade foils 12 were increased by a like amount in all aft half ofthe blade foils 12 on the elongated loop paths 13, then the aft portionof the craft 100 would rise. Imbalanced loads may be addressed in thismanner as well. Indeed, according to embodiments, situations in whicheither the aft or forward sections are more heavily loaded, may beaddressed by trimming changes of pitch angles of the blade foils 12 inthe affected area.

As alluded to above, the depicted shape of a fuselage 10 in the figuresshould not be interpreted as conveying any preferred shape thereof.Indeed, the depicted shape of the fuselage 10 is only meant to highlightthe potential compactness of the LPM assemblies 11, and is also meant toconvey the adaptability to roads and high-speed conventional surfacetravel, such as on normal roadways, highways and other off-road areas ofsurface travel, as well as for ease of loading, ingress and egress thata compact structure with such protected LPM assemblies 11 according toembodiments enables. According to embodiments, enhancements to intakemass flow may be achieved, with a combination of fuselage shape and anyducting elements associated with a fuselage, placement of the LPMassemblies 11, and inboard and outboard wing/ducting structures that maybe configured to augment funneling and directing of large masses ofairflow into the LPM assemblies 11, while also preventing or minimizingunfavorable phenomena common to vertical lift aircraft, such as, forexample, vortex regurgitation during certain phases of flight and hover.According to embodiments, wide center of gravity options are enabledadvantageously simply as a result of the placement of LPM assembliesincluding components imparting aerodynamic forces, being located at theperiphery of the load space. Likewise in combination with the ability toalter pitch angles to individual, sub-regions or whole LMU blade foils,these lifting units not only have maximum mechanical advantage by virtueof their outer edge placement, they also confer the benefit of producinglarge lifting forces brought to bear at specific points. Advantageously,according to embodiment, multiple relatively small lifting units (bladefoils) are placed all along the load space as bounded by fuselage 10,and their controllability gives an operator or operating system preciseoptions to deal with load asymmetries.

Embodiments enable the fine-grained control of blade foils. For example,segments or groups of blade foils 12 may be controlled independently ofother segments or groups of blade foils 12. Moreover, depending upon thecontrol mechanism, individual blade foils 12 may be independentlycontrolled. Described and shown herein are embodiments in which a groupof blade foils 12 may be controlled independently of other blade foils12. Other embodiments shown and described herein enable the control ofsubgroups or even individual blade foils 12, thereby enabling anunlimited number of control patterns to effectively allow for limitlesscombinations of lift, propulsion, maneuvering and attitude, each ofwhich may find utility in different situations. For example, controllingeach blade foil 12 individually may be carried out such that each bladefoil 12 is pivoted to a controlled pitch angle for a desired duration(defined, for example, in terms of a range of positions along elongatedloop path 13) or to a controlled pitch angle as the blade foil or bladefoils 12 arrive at or near a predetermined position along elongated looppath 13. These control inputs may be transmitted electronically,hydraulically, mechanically or in a variety of combinations for example.Indeed, according to one embodiment, as each blade foil 12 passes apredetermined location along elongated loop path 13, its pitch angle maybe controlled to be the same as or different from the preceding bladefoil 12. Ultimately, an overall pattern may be configured, preciselytailored and quickly altered under computer control, for example, inresponse to pilot or programmatic inputs and/or in response to changesin conditions, such that choreographed maneuverings may be achieved byentering a desired maneuver, or response to conditions (both stable andvariable) into a computer algorithm and then enabling computer controlof the pitch pattern(s) of the blade foils 12, elongated loop path 13speeds (including starboard elongated loop path(s) 13 relative to portside elongated loop path(s) 13) and engine power (in one embodiment, theengine power applied to each LPM assembly 11 may be independentlycontrolled and coordinated) to produce a desired flight effect or flightpath profile. One embodiment comprises more than one LPM assembly 11 perside of craft, and such LPM assemblies 11 may be disposed adjacent toone another horizontally, may be located in tandem, fore and aft(leading/trailing one another) stacked vertically, or nested within eachother, for example. As shown in FIG. 1, the blade foils 12 may bedisposed, according to one embodiment, in close proximity to fuselage10. This close proximity enables further functionality and advantages,as detailed herein below.

Advantageously, the forces acting upon each blade foil 12 are smallerthan the forces that would otherwise act on comparatively larger surfaceareas of conventional rotary of fixed wings. Each blade foil 12,therefore, carries only a small portion of the total load, and flightsmay be continued despite damage to or even loss of one or more bladefoils 12. Additionally, the close proximity of the aerodynamic surfacesof the blade foils 12 and their components to the fuselage 10advantageously minimizes their vulnerability, as compared to theaerodynamic surfaces of conventional fixed or rotary wings. This closeproximity and any protective structures added beneficially as a resultof the close proximity of an entire LPM assembly 11, in turn, acts toprotect occupants of the craft, as well as to protect surroundingstructures from damage as a result of contact with the fast moving bladefoils. Maneuvering in constrained areas is also greatly improved, ascompared to conventional fixed or rotary wing aircraft. Other advantagesof the present embodiments include ease of de-icing, enhanced protectionagainst bird strikes and other hazards, and the ability to use lessexotic materials for construction of aerodynamic surfaces, given thevastly decreased lever arm/moments that bear on these surfaces andstructures. Advantageously the close proximity of the blade foils 12 tothe fuselage 10 affords opportunities to incorporate other componentshaving fixed and/or movable surfaces such as fences, ducts, vanes,slots, slats, skirts, jets of bleed air and other aerodynamic entitiesinto the craft, according to embodiments. These components may beattached to the fuselage or other nearby structures, and/or coupled tothe blade foils 12 themselves.

According to further embodiments, the blade foils 12 may be configuredto follow elongated loop path 13 such that their respective leadingedges remain the same and, in the case of counter clockwise progressionaround a port side elongated loop path 13, these leading edges may befacing forward along the top portion of the path of elongated loop path13 whereas along the bottom portion they may be pointing aft. It may bemore favorable aerodynamically, particularly in forward and aft flighthowever, to keep the attitude of blade foils aligned with the horizontaldirection of flight, and for this reason, embodiments that account forthe majority of the illustrations and descriptions are configurationsthat change the leading edges of each blade foil 12 as each progressesalong elongated loop path 13 and particularly, at the ends of theelongated loop paths where blade foils 12 are controlled in such a waythat they remain aligned with relative flows. Having the leading edge ofthe blade foils 12 alternate as they progress along the top pathrelative to the bottom path of elongated loop path 13 enables each bladefoil to maintain its upper surface facing upwards and its lower surfacefacing downwards throughout the entire revolution thereof aroundelongated loop path 13. As a result, each phase of the cycle of theblade foils 12 around elongated loop path 13 may then, as well as theblade foil shapes and chords themselves, according to one embodiment, beoptimized for its or their particular function. The structures andmethods that enable alternating leading edges of blade foils 12, whilesimultaneously maintaining upper surfaces thereof on top, and lowersurfaces thereof on the bottom throughout a cycle are detailedhereunder. According to one embodiment, for forward travel, the edges ofblade foils 12 may be optimized for high speed forward flights toaccount for the much higher air speeds and shallower pitch angles on thetop of the elongated loop path 13 relative to the bottom half of theelongated loop path 133, according to one embodiment. Embodiments areconfigured to enable incorporation and/or optimization of sweep angles,edge slots, edge slats and including such features as blade foil 12 tipeffects including wing tip fences, shapes, vortex generators andwinglets among others. Another functionality of embodiments is thecapability to increase top speeds. Indeed, configuring the leading edgesof the blade foils 12 to be swept and/or extremely thin on the forwardmoving pathway (e.g., top portion) of elongated loop paths 13, mayenable even supersonic flight, due to the streamlining of the bladefoils 12 and the elimination of retreating blade stall, among otherlimitations. The structure of the blade foils 12 and the elongated looppaths 13 also enables the elimination of other undesirable phenomena,including blowback, dissymmetry of lift and other instabilities.

It should also be noted, referring to FIG. 1, that control assembliesmay be located outboard of LPM assemblies 11 as shown or mayadvantageously be located between LPM assemblies 11 and fuselage 10, maybe an integral part of fuselage 10 or may be disposed within fuselage10, according to embodiments. According to embodiments, otheraerodynamic structures to augment flow and/or lift effects among othersmay be added as desired given the configuration of the craft and theability to alter whole LPM assemblies 11 with respect to the rest of thestructure(s). Such structures may participate in configuration changesin addition to aerodynamic functionalities. Likewise, rotatingcomponents, now exposed to high relative airstreams, may be utilized forpropulsion, lift and maneuvering including pitch control.

FIG. 2 shows the functionality of shifting leading edges of blade foils12 along the upper portion of elongated loop path 13 paths and the lowerportion of elongated loop path 13. The leading edges of the blade foils12 traveling along the upper portion of the elongated loop path 13 in aforward direction along the direction of forward flight may be shaped orstreamlined for high relative flows (such as, for example, a truncateddelta wing pattern) and when these blade foils 12 reach the forward apexof elongated loop path 13, transitioning to the lower portion of anelongated loop path 13, the now leading edges, which were trailing whentraveling along the upper portion of elongated loop path 13, may nowassume a more traditional thick cord, high lift and more propulsive(e.g., higher drag) configuration. According to one embodiment, whenblade foils 12 reach the farthest aft location along elongated loop path13, they may, depending on their shape and chord, once again revert to amore laminar flow shape, either simply as a result of their direction oftravel relative to the direction of overall craft travel given the factthat leading and trailing edges of the blade foils 12 trade places,and/or as a result of more complex mechanisms utilized to createadditional changes based on angle of attack or coefficient of lift.Moreover, any other changes that contribute to either highly streamlinedconfigurations in the upper portion of elongated loop path 13 or highlift, high propulsion configuration in the lower portion of elongatedloop path 13 over aerodynamic surfaces in one region or another or both,with reference to elongated loop paths 13 to augment lift, drag(propulsion) or other effects such as diffusion of noise, heat or otherbyproducts of power generation and flight, are within the scope of theembodiments shown, described and claimed herein.

FIG. 3 shows control units 15, which may comprise elongated cone-shapedtracks whose curvature is followed by a plurality of control arms 20,each of which is coupled to a respective one of the plurality ofpivoting blade foils 12. In this manner, relative angles and distancesbetween the control unit 15 and the pivot points about which each bladefoil 12 pivots (best shown at reference 21 in FIG. 37), and the mannerin which the blade foils are constrained by driving tracks 14, maydictate individual pitch angles (and/or chord length) of each of theblade foils 12 as they progress around elongated loop path 13 accordingto embodiments. Other control configurations that achieve the same orsimilar comprehensive control of individual blade foils 12 around anelongated loop path may be envisioned, all of which are considered to bewithin the scope of embodiments herein. As shown in FIG. 3, the leadingedges 22 of the blade foils 12, which may comprise flaps or other liftenhancing components, may become the trailing edges of the blade foils12, as the blade foils 12 transition from the upper portion of elongatedloop path 13 to the lower portion thereof. Similarly, the trailing edgesof the blade foils 12 on the upper portion of the elongated loop path 13may become the leading edges of the blade foils 12 traveling on thelower portion of the elongated loop path 13 blade foil. Advantageously,blade foil edges, sweep angles and chord shapes and lengths may beoptimized for their respective roles as the blade foils 12 travel alongthe upper portion of elongated loop path 13 and as the blade foilstravel along the lower portion of the elongated loop path 13. That is,the blade foil characteristics may be dynamically and differentiallyadjusted for blade foils 12 travelling along the upper portion of theelongated loop path 13 and for blade foils 12 travelling along the lowerportion of the elongated loop path 13, such as during forward flight,(usually the direction of desirably higher speeds), hovering, attitude,climbing and cruising portions of common flight plans. Moving thecontrol units 15 in an inboard direction would, according toembodiments, move all blade foil angles along both upper and lowerportions of elongated loop paths 13 to lower pitch configuration. Incontrast, moving control units 15 in an outboard direction would,according to one embodiment, move all blade foil angles along both upperand lower portions of elongated loop path 13 to higher pitchconfigurations. Moving control units 15 upward relative to blade foilpivot points as located by attachments to driving tracks 14 would,according to one embodiment, decrease the pitch angles of the bladefoils 12 along the top portions of elongated loop paths 13 whileincreasing pitch angles of blade foils 12 along the bottom portions ofelongated loop paths 13, thereby causing the craft to move forwards.Moving control units 15 downward, according to one embodiment, may causethe opposite effect; namely to increase the pitch angles of the bladefoils 12 along the top portions of elongated loop paths 13 whiledecreasing the pitch angles of blade foils 12 along the bottom portionsof elongated loop paths 13 causing the craft to retreat. According toone embodiment, all attitudes, directional changes and altitude changesincluding speeds and rates may be made available by differentiallycontrolling the LPM assemblies 11.

FIG. 4 shows another embodiment of a control unit. In this case, thecontrol unit 15 may comprise a moving track control unit 15 with angledcontrol elements 17, which may be configured to raise and lower controlarm connecting followers 18 and control arms 20, which correspondinglyraise and lower the pitch angles of blade foils 12. The alternativeembodiments shown here include that the functionality andinterdependency of individual blade foils including their control armsrelative to control units 15 is ensured and demonstrated. Additionally,in this embodiment, high speed bearing components are not required forthe control arm followers 18 and these components, according to oneembodiment, may advantageously be constructed of low weight, low heattolerance materials. It should also be noted that the attachment pointof the through-blade foil elements 19 may be located at any point alongthe chord of the blade foil, according to embodiments.

FIG. 5 shows blade foils 12 positioned along the lower portion ofelongated loop paths 13, and demonstrates that movement of control units15 away from driving tracks 14 results in increasing the pitch angles ofthe blade foils 12 and moving control units 15 towards driving tracks 14results in decreasing the pitch angles of the blade foils 12 along thelower portion of elongated loop path 13, resulting in the same pitchchange directions as are effected by those same relative movements,control unit 15 to drive track 14, for the blade foils 12 along theupper portion of the elongated loop path 13, thereby resulting in a“collective” same-direction pitch change in the blade foils 12 travelingalong both upper and lower portions of elongated loop path 13. It shouldalso be noted that such pitch change mechanisms may easily be envisionedto change individual or a limited series of blade foil pitch angles atany point along the elongated loop path 13, according to embodimentsherein.

FIGS. 6, 7 and 8 are various views of the effects of moving control unit15 inwards (towards) relative to drive tracks 14, which are thecomponents that constrain the position of the blade foils and thusdetermine the pitch or angle of attack in space around elongated looppaths 13. Indeed, the pitch angles and other changes relative to bladefoils may be controlled, according to one embodiment, by changing therelative positions of control units 15 and drive tracks 14. FIG. 6 is aside view showing a control unit 15. In FIG. 7, control unit 15 isremoved to clearly show changes in the pitch of the blade foils 12 asthe blade foils 12 travel around elongated loop path 13. In FIG. 7, thepitch angles of the blade foils 12 are relatively “neutral” andapproximately of equal value in both the blade foils 12 traveling alongthe upper portion of elongated loop path 13 and for blade foils 12traveling along lower portion of the elongated loop path 13. Such aconfiguration may be suited, according to one embodiment, to a hoverconfiguration or at least a configuration in which the horizontal motionof the craft is stable, and in which vertical positioning or change inaltitude may be determined by the power delivered to the LPMassembly(ies) 11 on the port and starboard sides, as well as loads andload distributions. Likewise, FIG. 8 is a front view of a craftaccording to one embodiment that shows only a portside LPM assembly 11,with its control unit 15 removed for clarity. In this view, control arms20 are shown in relatively neutral or at rest positions, similar to thepitch angles they dictate for blade foils 12, according to embodiments.In this position, the control arms are simply following their patharound the outside, expanded section of control unit 15, which is as aresult of control unit 15 being moved in, towards fuselage 10.

FIGS. 9, 10 and 11 are similar views to those shown in FIGS. 6, 7 and 8,and show the effects of moving control unit 15 farther away from bladefoils 12 locating attachments on drive units 14, and thus, in thisembodiment, farther away from fuselage 10. Indeed, moving control unit15 farther away from blade foils 12 locating attachments on drive units14 collectively increases the pitch angles of control arms 20 and theirattached blade foils 12. This effect may be envisioned by comparing thepositions of the control arms 20 of FIG. 11 to FIG. 8. In FIG. 11, thecontrol arms are effectively all squeezed together towards the middle asa result of the constraint of the control unit “cone” being moved awayfrom the fuselage 10, resulting in increased pitch of all blade foilsalong the elongated loop path 13. It should also be noted that,according to embodiments, control units 15 of the individual LPMassemblies may also be moved inwards and/or outwards as well as up ordown in equal or differential distances at their forward ends and aftends. Alternatively, the control units 15 may be moved only at theforward or aft ends including any combination of relative movementsthereof, which then causes a selected, controlled increase or decreasein control arm-induced blade foil pitch in selected portions of theelongated loop path 13. For example, a control unit 15 may be moved awayfrom drive track blade foil locating attachments at the forward end ofone LPM assembly 11 while moving the aft end towards blade foil 12attachments, thus creating differential “collective” control of bladefoils, forward relative to aft. In this instance, such differentialcollective control of the blade foils increases pitch in forwardlylocated blade foils 12 along both the upper and lower forward portionsof elongated loop path 13, while simultaneously decreasing the pitchangles thereof aft along both upper and lower portions of aft elongatedloop path 13, resulting in a raising of the nose of the craft, accordingto embodiments. In other words, according to embodiments, moving controlunits 15 towards blade foils' constraining components on drive track 14decreases pitch. Conversely, moving control units 15 away from bladefoils' constraining components on drive track 14 increases the pitchangles of the blade foils “collectively” along both upper and lowerportions of elongated loop path 13.

According to embodiments, the control units 15 may be moved towards oraway from the fuselage 10. Also according to embodiments, the controlunits 15 may be moved up or down relative to the fuselage 10. Combinedmovements toward, away, up or down may be carried out, according toembodiments. Indeed, any of these movements may be carried outindependently of one another relative to the forward or aft end of eachLPM assembly 11. FIGS. 12, 13 and 14 are similar views showing theeffects of raising the position of control units 15 relative toattachment/pivot points for blade foils 12, which causes the pitchangles of the blade foils 12 to increase along the lower portion ofelongated loop path 13, with a corresponding decrease in or neutralpositioning of pitch angles of the blade foils 12 along the upperportion of elongated loop path 13. Such a configuration would, accordingto one embodiment, cause the craft to move forward. Alternatively,making these changes to control unit 15 positioning on only a port sideLPM assembly would cause a craft according to embodiments to rotate tostarboard (and may also automatically bank to starboard as well,depending on power input to port LPM assembly relative to starboard LPMassembly) in the horizontal plane. FIG. 14 illustrates this by showingthe control arms 20 along the upper track and lower track being raised,resulting in flatter pitch of the blade foils 12 along the upper portionof elongated loop path 13 and increased blade foil pitch along the lowerportion of elongated loop path 13, resulting in forward and/or climbingflight.

FIGS. 15, 16 and 17 show the effects of lowering control units 15 as awhole, causing the pitch angles of the blade foils 12 to increase alongthe top portion of elongated loop paths 13 and to simultaneouslydecrease the pitch angles of the blade foils along the lower portions ofelongated loop paths 13. The effect of such a configuration would be tocause a craft according to embodiments to retreat backwards and,assuming adequate power input, climb in reverse direction relative tothe forward orientation of the craft. Alternatively, if these controlinputs are applied only to port side LPM assembly(ies) 11, a craftaccording to embodiments would tend to rotate (port side retreats) andalso bank to port. Thus, comparing inputs shown in FIGS. 12, 13 and 14with those shown in FIGS. 15, 16 and 17, it may be recognized thatturning (and banking if desired) a craft to port according toembodiments may be carried out in several ways, including backing theport side up or, alternatively as desired, advancing the starboard side.According to embodiments, both of these may be carried out whiledifferentially elevating or lowering the height of port side relative tostarboard side with simple inputs and control mechanisms. Again, itshould be noted that individual control units 15 may be moved up, down,in, or out at their forward or aft loci, resulting in a continuum ofcontrol options affecting individual blade foils at any point on theelongated loop path(s) 13.

FIGS. 18 and 19 show yet another configuration with regard to changes invertical positioning of control units 15 relative to attachment pointsof blade foils 12. In this case, the forward ends and aft ends ofcontrol units 15 may be differentially raised and/or lowered relative tothe attachment points of the blade foils 12, thereby causing iterationsof control including nose high or low, aft high or low as well astwisting attitudes and flight patterns. According to embodiments and asshown in, for example, FIGS. 6 through 19, inwards and outwardsmovements of whole LPM assemblies 11 or ends of LPM assembly(ies) 11 aswell as upwards and downwards movements may be smoothly combined withrelative and/or whole craft power changes to bring about limitlesscontinuums of configurations, craft attitudes (including stable upsidedown, right side up, along with permutations thereof) as well as variousindividual or combined movements including hovering, banking, twisting,pivoting horizontally and vertically, climbing, diving, forward,reverse, and sideways movements in a continuum of speeds in theseindividual or collective directions, or collections thereof, accordingto embodiments, and also compensate for load and trim factors of thecraft, as desired.

FIGS. 20 and 21 are illustrations of a single LPM assembly 11 in twodifferent configurations. FIG. 20 shows an LPM assembly 11 whose bladefoils 12 may be provided with their leading edge high lift devices 22,such as automatically deploying slats, for example, and trailing edgehigh lift devices 23 arranged along the top portion of elongated looppath 13 of an LPM assembly 11 shown not deployed, and therefor incompact configuration, in short span, and in entirely swept leading edgeconfiguration. Such a configuration may be suited to, for example, ahigh speed, low altitude flight mode. As also illustrated clearly inFIG. 20, in one embodiment, the blade foils 12 may be configured topresent swept leading edges along the top portion of the elongated looppath 13 and a more perpendicular leading edge along the bottom portionof the elongated loop path 13 as leading edges are effectively exchangedas the blade foils transition from the upper portion to the lowerportion of the elongated loop path 13. An additional configuration asillustrated in FIG. 21 shows these blade foils 12 in an extended spanconfiguration, which maximizes surface area for increased lifting,propulsion and maneuvering capabilities as well as efficienciesassociated with such increases in aspect ratios. Such a high aspectratio configuration may be suited, for example, to high power, low speedflight mode (and may be well suited for lifting heavy loads) or for highaltitude, high speed, high efficiency and low power flight modes. Theblade foils 12 may be actuated and caused to assume these configurationsin any number of ways. For example, internal pressure changes may becommanded by the pilot and/or programmatically, or such configurationsmay be effected automatically in response to ambient pressure changeswith respect to internal pressures such as, for example, in lowerpressure, high altitude conditions and/or during flights with additionallow density altitude factors present.

According to one embodiment, one or more blade foils 12 may be removedas desired to adapt to certain conditions, such as reduced poweravailability. Conversely, according to one embodiment, blade foils 12may be added. Such added blade foils 12 may be of the same or differentspecifications compared with the existing blade foils 12 at any point(s)along the elongated loop path 13.

FIGS. 22 through 24 show one embodiment of a craft comprising statorvanes 33. Such stator vanes 33 are representative examples of flowdirecting devices that may be fixed or movable and that may beconfigured to confer protective shielding effects for moving componentssuch as blade foils 12, control arms 20, control units 15 and drivingtracks 14, as well as other supporting, driving and directingcomponents. Such additional components may include, for example,longitudinal wings, ducts, skirts, fences and the like. Moreover,according to embodiments, devices such as endplates and winglet-typestructures may be provided, either on or near the blade foils 12. Thestator vanes 33 shown in FIGS. 22-24 may be provided and disposed above,below and between constituent structures of the LPM assemblies 11. Thestructure and emplacement of the stator vanes 33 in FIGS. 22-24 areshown according to anticipated flows. However, the angles thereof or anyangles as shown in FIGS. 22-24 are not to be considered as limiting, asthose of skill in this art may recognize that there are a wide varietyin terms of numbers, shapes, orientations, locations and combinations ofdevices such as these that are enabled by compactness, configuration andproximity of LPM assemblies 11 with respect to the fuselage 10 of acraft according to embodiments. These stator vanes 33, which may bestatic or dynamically movable, as well as other aerodynamic componentsmay direct flows to combat or neutralize recirculation, to optimizeflows between upper and lower sections of LPM assemblies 11 and may alsofunction to reduce noise, heat signature, turbulence, dust clouds andother unwanted conditions or byproducts. The stator vanes 33 may,according to one embodiment, be used for trimming purposes, for changingmission capabilities, efficiencies and for any other use, includingcountering of column settling and other ground effects encountered withlow altitude hovering situations. The stator vanes 33 may also act asbumpers, may act as deflectors and/or may serve other safety needsincluding enabling flights right up to and even against fixed objects,including landing zones and structures. According to embodiments, thestator vanes 33 may also protect the moving elements of the craft fromwildlife, wires and other encountered potentially hazardous objects andmay also protect these elements from damage and/or destruction as aconsequence of encountering another craft. Similarly, combinations ofcraft, either linked or independent of one another, according toembodiments herein may be used for joint accomplishment of certainmissions, including coordinated lifting of objects, surveying or othermissions.

FIG. 25 is an underside perspective view of an alternate configurationof an LPM assembly 11 showing drive track 14, blade foils 12 withleading edges 16 and control tines 34, according to one embodiment. FIG.26 is an underside perspective view of such an alternate configurationof an LPM assembly 11 showing drive track 14, blade foils 12 withleading edges 16, and control tines 34, according to one embodiment.Also shown are partial upper and lower portions of elongated cone-effectcontrol track, according to one embodiment. FIG. 27 is a side view linedrawing of an alternate configuration of an LPM assembly 11 of FIG. 25,showing forward fairing 35 and aft 36 fairing, according to oneembodiment. Indeed, FIGS. 25-27 show an alternative configuration forLPM assemblies 11 and controlling components for a craft according toembodiments, as well as fairings 35, 36 that find utility where theblade foils 12 may not be aligned with flows associated with forward andbackwards flights, such as in transition zones at the forward and aftextremes of LPM assemblies 11. FIG. 25 shows blade foils 12 that, incontrast with other embodiments described and illustrated herein, do nottrade leading edges for trailing edges as they circulate aroundelongated loop paths 13. Instead, in these configurations, the bladefoils 12 maintain the same leading edges all the way around elongatedloop paths 13, but may still be controlled similarly to otherembodiments described herein. Significantly, however, upper surfaces ofblade foils 12 positioned along upper segments of elongated loop path 13become lower surfaces as they transition around to the lower portion ofthe elongated loop path 13. While this embodiment may be configured tomaintain leading edges and trailing edges constant all the way aroundelongated loop path 13, this embodiment does not maintain alignment withrelative flows and does not keep upper surfaces of the blade foils 12 ontop and lower surfaces of the blade foils 12 on the bottom all the wayaround elongated loop paths 13. Control mechanisms may be slightlyaltered relative to other control mechanisms described and illustratedherein. According to one embodiment, a control mechanism may compriseangled control tines 34, which may be attached to controlling arms foreach individual blade foil 12. The angled tines 34 may be made of orcomprise lightweight materials and may be streamlined for minimal drag.As such, the control times 34 may also serve as additional aerodynamicsurfaces configured in winglet-type shapes.

According to one embodiment, a control method may comprise the controltines 34 interacting with constraining elongated loop paths 13 attachedto a control belt unit 15, as described relative to other embodimentsherein. According to one embodiment, moving the control belt 15 towardsand away from blade foils 12 alters their respective pitch angles on theupper portions relative to the pitch angles of the blade foils 12 onlower portions of elongated loop path 13. Moving control belt 15 upwardsand downwards with respect to the pivot points of blade foils 12 causescollective changes to the blade foils 12 along both top and bottomportions of elongated loop paths 13. Thus, in this configuration andaccording to one embodiment, moving control belts 15 closer and fartherfrom blade foil anchoring points in drive track 14 result in effectssimilar to the effects previously described herein for anotherembodiment, which in that case results from moving control elements upand down relative to blade foil pivot points. In other words, theeffects are similar for each embodiment, however moving control elementin and out changes pitch in all blade foils in one embodiment while inthe embodiment in FIG. 26, by virtue of leading edges remaining leadingat all points around elongated loop path 13, moving control element inand outwards changes upper and lower blade foils differentially relativeto one another. In the same way, elevating and lowering control units inthe embodiments previously described herein cause differential pitchchanges upper elongated loop path blade foils relative to lowerelongated loop path blade foils, whereas in an embodiment of FIG. 27,these control element movements cause collective changes to all bladefoil units on the upper as well as lower elongated loop path 13.According to one embodiment, these effects may easily be counteracted bychanging where control tines 34 are located with respect to pivot points(shown at reference 27 in FIG. 37) of blade foils 12 such that thecontrol arms are located near the leading edges 16 of blade foils 12rather than near the trailing edges as they are shown in FIGS. 25, 26and 27.

FIG. 27 shows examples of fairings 35, 36 at the forward end and aftend, respectively, of an LPM assembly 11 according to one embodiment.The fairings 35, 36 may be configured, according to one embodiment, tostreamline the entire LPM assembly(ies) 11 by directing flows such thatthe entire LPM assembly 11 has a wing shape to augment lift and toshield the blade foils 12 in the transition areas where they are notaligned with incoming and exiting flows at the ends of LPM assemblies 11during forwards and/or backwards flight directions. It should be notedthat such fairings may be used with blade foil/LPM assemblyconfigurations corresponding to either constant leading edge or changingleading edge with respect to the blade foils. According to oneembodiment, the fairings 35, 36 may be movable (e.g., for controllingand/or trimming purposes) and additionally may be used as protectiveelements and as deflectors for wildlife, debris and structures that maybe encountered during operations.

FIGS. 28 through 34 show embodiments in which entire LPM assembly(ies)11 are configured to selectively move away from the fuselage 10 at aselectable angles. Embodiments may also utilize the driving track wheelelements as fans as shown at reference 31 to enhance flows while innormal position. Moreover, such driving track wheel elements 31 withinthe LPM assemblies 11 may be fully or partially aligned with thefuselage 10 in a “feathered” configuration, such that the driving trackwheel elements 31 are configured as disc fences or airflow barriers thatkeep flows relatively confined within an LPM assembly 11 between upperand lower blade foils. The driving track wheel elements 31 may also bedeployed as components of integrated power units such as turbofans wherethey may be configured as bypass fans by themselves or in conjunctionwith blade foils 12. FIG. 29 shows such fan elements located only on theoutboard side of LPM assemblies with interspersed idler wheels 38.However, they may be located on the inboard side or both inboard andoutboard areas, according to embodiments. As LPM assemblies 11 arefurther splayed outwards (for example) at the forward ends, the drivingtrack wheel elements 31 may be exposed to flows associated with forward(and/or reverse) flight directions and may then take on additionalpropulsive roles as suggested in FIG. 29. Though LPM assemblies 11 areshown splayed outwards at the forward end of the craft shown in FIG. 28,they may also be splayed out at the aft end instead. Whether aft orforward, the degree to which the LPM assemblies 11 are splayed outwardsmay be different on the starboard side as on the port side, for afine-grained control of drifting and for trimming for relative winds,for example, among a variety of useful functionalities. FIG. 30 is anoverhead view of LPM assemblies 11 in position against a fuselage 10prior to deployment outwards and also illustrates the effect ofincluding multiple stator vanes 33, which leads to near completeprotection of blade foils 12, according to embodiments.

FIG. 31 shows a craft according to one embodiment, comprising LPMassemblies 11 that are configured to symmetrically (or asymmetrically,to some extent) splay outwards at the forward ends. In the farthest leftillustration, lift is accomplished almost entirely by LPM assemblies 11along the entire length of the fuselage 10 with some possiblecontribution from fuselage flows, while propulsion is still directed aftby at least the blade foils 12 of the LPM assemblies with possibleadditional contributions from fan drive wheels 31, as described above.In the middle illustration, additional movable wing strut elements 37(not necessarily drawn to scale) are exposed by virtue of their aftattachments sliding forwards. The illustration also shows how themovable wing strut elements 37 may be positioned to contributesignificant lift, control and structural as well as aerodynamicstability, according to embodiments. The movable wing strut elements 37are shown with “flaperons” 40 that are configured to have at least someof the functionality of both flaps and ailerons. In the far rightillustration of FIG. 31, the movable wing strut elements 37 are shown tobe both retracted slightly and extended in span such that LPM assemblies11 are now in a position “over center” while the movable wing strutunits 37 are shown in a highly swept configuration, which may be wellsuited to high speed flights, where at least a portion of the propulsionmay be provided by fan drive wheels 31, while the blade foils 12 of theLPM assembly 11 may be configured to provide lift, directional control,and pitch control in conjunction with, or independently of, movable wingstrut elements 37, according to embodiments.

FIGS. 32, 33 and 34 show various perspective views of a craft accordingto one embodiment in which the LPM assemblies 11 may be spayed to aselectable degree. FIG. 34 shows one embodiment of such a craftcomprising a slide track 41 along the lower side of fuselage 10configured to enable the aft ends of the movable wing struts elements 37to slide forward as LPM assemblies 11 are deployed outwards at theforward ends. Such a configuration according to one embodiment enablesthe movable wing strut elements 37 to gradually assume lift and controlresponsibility, particularly for forward loads while LPM assemblies 11deploy, in effect, backwards relative to the craft's center of gravity.According to one embodiment, the movable wing strut elements 37 may bealigned with flow in their “tucked away” position along the side offuselage 10 whether they are horizontally oriented or verticallyoriented or somewhere in between.

FIG. 35 illustrates one embodiment in which the LPM assemblies 11 may becanted, for example, LPM assemblies outwards at the lower sides, awayfrom fuselage 10. If symmetrically deployed, such canted LPM assemblies11 may exhibit a substantial stabilizing effect on the craft. Ifcontrolled asymmetrically, such canted LPM assemblies 11 may combatdrift, may be used for landing and/or takeoff from slopes and forstandoff purposes when operating near structures. The canted LPMassemblies 11 may also combat recirculation and may direct flows awayfrom occupants and/or structures on the ground, as may be desirable, forexample, during emergency and/or rescue operations. Moreover, the cantedLPM assemblies 11 may also find utility in directing flows to blowsmoke, debris or other elements including liquids, gases, wildlife orothers. Canting inwards at the bottom may be used to create an enhancedcushion, which when coupled with the flow skirts, fences, ductingstructures, stator vanes of fixed or movable variety described herein,may be used to enhance low energy hovering and/or movement over surfacessuch as ice, water sand and/or vegetation, while controlling dispersionof these elements as well as air thus accumulated. For example, such acapability may be well suited to landing operations as well as duringtransitional operations such as heavy lifting or transitioning tohigh-speed flights. Canting inwards or outwards at the topsides mayproduce similar and/or additional functionalities and are likewisewithin the scope of embodiments.

FIGS. 36 and 37 show the dynamically configurable nature of the bladefoils 12, according to embodiments. Such dynamic configurability may beeffected on individual blade foils, on groups of blade foils (e.g., onthe bottom portion of elongated loop path of on the top portion ofelongated loop path 13 or segments of such portions) or among all bladefoils 12 at once. FIGS. 36 and 37 illustrate changes to the chordthickness of the blade foils along the lower portion of elongated looppath 13 in a port side LPM assembly 11. In FIG. 36 blade foils 12 alongthe bottom portion of a port side LPM assembly 11 are noticeably thickerin chord relative to their counterparts along the top portion of thesame LPM assembly 11, which illustrates the changes that occur as aresult of changes to the pitch of the control arms affecting, the crosssection of the blade foils 12. This example utilizes changes to thepitch angle to also effect other changes that contribute to high liftand high propulsion, particularly in the instance where forward travelslows relative travel through the air of retreating blade foils 12 alongthe bottom portions of elongated loop path 13. It should be noted thatblade foils 12 circulate from back to front along the top of an LPMassembly and front to back along the bottom of an LPM assembly in theillustrations included herein. For clarity, however it is to beunderstood that the direction of travel of the blade foils 12 may bereversed, without departing from the embodiments described and shownherein. FIG. 36 shows chord thickness changes with changes in pitchangles. However, other changes may occur based on positions of bladefoils 12 along elongated loop paths 13. Other changes may includeautomatic or manual deployments of slats, flaps, fenestrations and thelike, as well as geometric changes that may be caused to occur bychanging the angle of attack relative to flows occurring along topand/or bottom portions of elongated loop paths 13. Some of these changesmay be effected through changes in flow patterns as directed by movablestator vanes, among other possibilities.

FIG. 37 shows further details of one embodiment, in which changes toblade foils changes may be effected by mechanical component. As shown, acamber adjusting cam 50 may be affixed to a control arm 20 to increasechord thickness when the eccentric shape of the camber adjusting cam 50wedges against internal surfaces of a blade foil 12, which also createsa sliding of upper versus lower surfaces of blade foil 12. Such slidingmotion may deploy leading edge slats 24, trailing edge thins 25 and/ormay expose openings creating the functional deployment of such high-liftdevices. Likewise, other high-lift configurations may be deployed, suchas openings to enable higher angle of attack of retreating blade foilswhile energizing upper surface airflow to prevent and/or delaystagnation, turbulence, loss of laminar flows and stalling of individualand/or groups of blade foils, according to embodiments.

A craft, according to embodiments, may be configured to move through afluid medium. The fluid medium may comprise, for example, air or water.The craft may be configured as a heavier than air craft. Alternatively,the craft may be configured to be lighter than air, by fitting the craftwith, e.g., helium gas-filled compartments. In such a case, the LPMassemblies 11 may be principally configured for maneuvering andpropulsion.

The craft, according to embodiments, may be configured with mechanicallinkages between a control yoke and the LPM assemblies 11. Alternativelyand according to one embodiment, the coupling may comprise a fly-by-wiresystem. The craft may be configured to be autonomously orremotely-piloted. The craft may be configured, therefore, as a pilotedcraft or as a remotely piloted, semi-autonomous or fully autonomousdrone. The present embodiments, its components and methods of use may beused separately or in any number of combinations with each other.Likewise, individually or in combination with each other, many of thecomponents and methods may be used in numerous applications beyond thedescribed primary use of highly maneuverable flight, including verticaltakeoff and landing. For example, the components, subassemblies, controlsystems, aerodynamic systems, methods of powering and adaptive controlusing power direction alone and/or in combination with aerodynamicsurfaces described and shown herein may be readily applied, as describedherein or modified, to applications other than flight.

While certain embodiments of the disclosure have been described, theseembodiments have been presented by way of example only, and are notintended to limit the scope of the disclosure. Indeed, the novelmethods, devices and systems described herein may be embodied in avariety of other forms. Furthermore, various omissions, substitutionsand changes in the form of the methods and systems described herein maybe made without departing from the spirit of the disclosure. Theaccompanying claims and their equivalents are intended to cover suchforms or modifications as would fall within the scope and spirit of thedisclosure. For example, those skilled in the art will appreciate thatin various embodiments, the actual physical and logical structures maydiffer from those shown in the figures. Depending on the embodiment,certain steps described in the example above may be removed, others maybe added. Also, the features and attributes of the specific embodimentsdisclosed above may be combined in different ways to form additionalembodiments, all of which fall within the scope of the presentdisclosure. Although the present disclosure provides certain preferredembodiments and applications, other embodiments that are apparent tothose of ordinary skill in the art, including embodiments which do notprovide all of the features and advantages set forth herein, are alsowithin the scope of this disclosure. Accordingly, the scope of thepresent disclosure is intended to be defined only by reference to theappended claims.

What is claimed is:
 1. A method, comprising: providing a fuselage;coupling a first lifting assembly to the fuselage, the first liftingassembly comprising at least one blade foil and an elongated loop paththat comprises a first portion and a second portion; generating lift tothe fuselage by causing the at least one blade foil to travel around theelongated loop path such that a leading edge of the at least one bladefoil travelling along the first portion of the elongated loop pathbecomes the trailing edge as the at least one blade foil travels alongthe second portion of the elongated loop path.
 2. The method of claim 1,further configuring manipulating the first lifting assembly to providemaneuvering and propulsion.
 3. The method of claim 1, wherein generatinglift is carried out in a fluid comprising at least one of air and water.4. The method of claim 1, further comprising dynamically controlling atleast one of a pitch and a chord of the at least one blade foil as theat least one blade foil travels along the elongated loop path.
 5. Themethod of claim 1, wherein coupling comprises coupling the first liftingassembly to one side of the fuselage and wherein the method furthercomprises coupling a second lifting assembly to another side of thefuselage.
 6. The method of claim 5, further comprising independentlycontrolling and moving each of the first and second lifting assembliesrelative to the fuselage.
 7. The method of claim 1, further comprisingcoupling the at least one blade foil to a control assembly that isconfigured to control a configuration of the at least one blade foil asthe at least one blade foil travels around the elongated loop path. 8.The method of claim 7, wherein the control assembly comprises, for eachof the at least one blade foil, a control arm, and wherein the methodfurther comprises the control arm changing at least one of a chord and apitch of the blade foil to which the control arm is coupled.
 9. Themethod of claim 8, wherein the control assembly comprises an elongatedcone-shaped control track defining a curvature and wherein the methodfurther comprises causing each control arm to follow the curvature ofthe elongated cone-shaped control track.
 10. The method of claim 9,further comprising configuring the control assembly to selectively movethe control track in all directions about x, y and z axes andconfiguring the control assembly to control at least of the chord andpitch of each blade foil by selectively moving the control track alongthe x, y and z axes thereof.
 11. The method of claim 3, wherein couplingcomprises configuring the elongated loop path of the first liftingassembly to be ovaloid-shaped.
 12. A method, comprising: providing afuselage; providing and coupling a first lifting, propulsion andmaneuvering (LPM) assembly to one side of the fuselage, the first LPMcomprising a first elongated cone-shaped control assembly that comprisesa first elongated loop path, a plurality of first angled controlelements and a plurality of first blade foils, each of the plurality offirst blade foils being coupled to the first control assembly by arespective one of a plurality of first control arms; causing each of theplurality of first blade foils to travel around the first elongated looppath; and controlling, as the plurality of first blade foils travelaround the first elongated loop path, a configuration of the pluralityof first blade foils as the plurality of first control arms follow acurvature of the first control assembly.
 13. The method of claim 12,further comprising providing and coupling a second LPM assembly toanother side of the fuselage, the second LPM comprising a secondelongated cone-shaped control assembly that comprises a second elongatedloop path, a plurality of second angled control elements and a pluralityof second blade foils, each of the plurality of second blade foils beingcoupled to the second control assembly by a respective one of aplurality of second control arms; causing each of the plurality ofsecond blade foils to travel around the second elongated loop path; andcontrolling, as the plurality of second blade foils travel around thesecond elongated loop path, a configuration of the plurality of secondblade foils as the plurality of second control arms follow a curvatureof the second control assembly.
 14. The method of claim 13, furthercomprising independently moving the first and the second LPM assembliesrelative to the fuselage.
 15. The method of claim 12, further comprisingcontrolling at least one of a pitch and a chord of the plurality offirst blade foils.
 16. The method a claim 12, further comprisingconfiguring the first LPM assembly to be selectively movable relative tothe fuselage in all directions along x, y and z axes.
 17. The method ofclaim 12, further comprising controlling the configuration of the firstblade foils by causing, for each of the first blade foils, a control armto follow a curvature of the first control assembly.
 18. The method ofclaim 12, further comprising independently controlling a configurationof individual ones, groups of or all of the first blade foils.
 19. Themethod of claim 12, wherein the first elongated loop path comprises afirst portion and a second portion and wherein the method furthercomprises controlling the first blade foils such that leading edges ofthe first blade foils travelling along the first portion of the firstelongated loop path become trailing edges as the first blade foilstravel along the second portion of the first elongated loop path. 20.The method of claim 12, wherein the first elongated loop path comprisesa first portion and a second portion and wherein the method furthercomprises maintaining leading edges of the first blade foils travellingalong the first portion of the first elongated loop path as leadingedges as the first blade foils travel along the second portion of thefirst elongated loop path.
 21. The method of claim 12, furthercomprising configuring the first LPM to operate in a fluid mediumcomprising at least one of air and water.
 22. The method of claim 12,further comprising configuring the first elongated loop path to beovaloid-shaped.
 23. A craft configured to move through a fluid medium,comprising: a plurality of first blade foils configured to move along afirst elongated loop path defined adjacent a first side of a fuselage;and a plurality of second blade foils configured to move along a seconddonated loop path defined adjacent a second side of the fuselage,wherein at least one of a movement and attitude of the craft within thefluid medium is controllable by controlling a configuration of theplurality of first and second blade foils.
 24. The craft of claim 23,wherein the plurality of first blade foils are disposed around the firstelongated loop path such that each leading edge of each of the pluralityof first blade foils is adjacent to and substantially parallel with atrailing edge of a next adjacent first blade foil.
 25. The craft ofclaim 23, wherein leading edges of the plurality of first and secondblade foils travelling along first portions of the first and secondelongated loop paths, respectively, are configured to become trailingedges as the plurality of first and second blade foils travel alongsecond portions of the first and second elongated loop paths,respectively.
 26. The craft of claim 23, wherein leading edges of theplurality of first and second blade foils travelling along firstportions of the first and second elongated loop paths, respectively, areconfigured to be maintained as leading edges as the plurality of firstand second blade foils travel along second portions of the first andsecond elongated loop paths, respectively.
 27. The craft of claim 23,wherein the plurality of first and second blade foils are configuredsuch that at least one of a pitch and chord thereof is controllable. 28.The craft of claim 23, wherein a configuration of groups or individualones of the plurality of first and second blade foils are independentlycontrollable.
 29. The craft of claim 23, further comprising: firstelongated cone-shaped control assembly defining a first curvature andcomprising angled a plurality of first control elements disposed on thefirst side of the fuselage; a first plurality of control arms, eachcoupled to a respective one of the plurality of first blade foils,configured to follow the first curvature; a second elongated cone-shapedcontrol assembly defining a second curvature and comprising a pluralityof second angled control elements disposed the second side of thefuselage; and a second plurality of control arms, each coupled to arespective one of the plurality of second blade foils, configured tofollow the second curvature.
 30. The craft of claim 23, wherein theconfiguration of the first blade foils is configured to be controllableindependently of the configuration of the second blade foils.
 31. Thecraft of claim 23, wherein: the plurality of first blade foils areconfigured and controllable to assume first configurations whiletravelling along a first portion of the first elongated loop path and toassume second configurations while travelling along a second portion ofthe first elongated loop path; and the plurality of second blade foilsare configured and controllable to assume first configurations whiletravelling along a first portion of the second elongated loop path andto assume second configurations while travelling along a second portionof the second elongated loop path.
 32. The method of claim 23, whereinthe first blade foils form part of a first lifting, propulsion andmaneuvering (LPM) assembly coupled to the first side of the fuselage andwherein the second blade foils form part of a second LPM assemblycoupled to the second side of the fuselage, and wherein a position andorientation of each of the first and second LPM assemblies iscontrollable relative to the fuselage.
 33. The method of claim 32,wherein the first and second LPM assemblies are controllableindependently of one another.